CN103237971B - Method for running fixed gas turbine, for device that the operation of gas turbine is adjusted and generating equipment - Google Patents
Method for running fixed gas turbine, for device that the operation of gas turbine is adjusted and generating equipment Download PDFInfo
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- CN103237971B CN103237971B CN201180057654.2A CN201180057654A CN103237971B CN 103237971 B CN103237971 B CN 103237971B CN 201180057654 A CN201180057654 A CN 201180057654A CN 103237971 B CN103237971 B CN 103237971B
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- fuel
- gas turbine
- transported
- pressure
- volume
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/38—Control of fuel supply characterised by throttling and returning of fuel to sump
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/46—Emergency fuel control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
- F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
- F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
- F05D2270/092—Purpose of the control system to cope with emergencies in particular blow-out and relight
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Feeding And Controlling Fuel (AREA)
- Control Of Turbines (AREA)
Abstract
The present invention relates to being used for running gas turbine（40）Method, for gas turbine（40）Startup or the device that is adjusted of operation（60）And generating equipment（42）.Although fuel network（13）Supply pressure only smaller, but in order to start gas turbine during, gas turbine can be realized when fuel changes or in removal of load（40）Safe operation and propose, volume of fuel（BV）It is provided with and fuel network（13）In supply pressure compare the pressure for significantly improving, and briefly convey from fuel network if necessary（13）The fuel of extraction（B）For improving the pressure of the fuel.By providing higher fuel pressure, pilot flame can burn under the ruuning situation for needing in a stable manner.Although by fuel network（13）The supply pressure for enduringly providing is less, but can also avoid thermoacoustics vibration and fray-out of flame.
Description
Technical field
The present invention relates to a kind of method for running fixed gas turbine, with following step：
- gaseous fuel is constantly extracted from fuel network, and
- add combustion air in the case of at least one combustor of gas turbine burning fuel.Additionally, this
Bright it is related to a kind of device for being adjusted to the operation of gas turbine.Finally, the present invention relates to one kind includes having at least
The generating equipment of the gas turbine of one combustor and compressor, wherein by the combustion air provided by compressor and can be from fuel
The fuel that net is persistently extracted is transported to combustor.
Background technology
Known in the state of the art there is fixed gas turbine and for running the wide of the method for gas turbine from available
General species and mode.The gas turbine for producing electric energy of modern configuration generally have can axial-flow type compressor, one
Or multiple combustor and turbine unit.Operationally, the fuel of combustor is transported to by means of the environment by compressor compresses
Air burning is steam, and the steam is expanded in the way of doing work in turbine unit on the rotor of gas turbine.Then,
Rotor drives and is converted into electric energy and is fed into the electromotor that electric current distributes in net mechanical energy low-loss.
When gas turbine starts, the rotor of the gas turbine is brought to fire speed by means of driving means, thus
The pilot fuel flow is lighted by pilot fuel flow is fed in combustor.Subsequently, pilot flame alight is via independent
Burner and/or burner be also injected to the main fuel flow in combustor.Meanwhile, driving means are decoupled with rotor.Then, rotor
Only also driven by the steam produced in burning.As running speed reaches 3000min most of the time-1Or 3600min-1, combustion
The start-up course of gas-turbine terminates.Subsequently, electromotor and electric current can be made to distribute the net Frequency Synchronization of net and by the generating
Machine is connected.
By pilot fuel and delivery of main fuel to corresponding burner or nozzle via separate work, be provided with valve
Tubing carry out, by means of volume and its pressure that the valve can adjust the fuel for correspondingly conveying.
In this as fuel, not only using liquid and also use gaseous fuel.In order to produce spy in a combustion chamber
The burning of not effective and low emission is known that the burning for continuously facilitating main fuel quality stream by pilot flame.As
Pilot fuel is usually used fuel gas, such as natural gas.
Due to needing a large amount of fuel, the fuel pipe system of gas turbine to be typically connected to fuel to produce a large amount of electric energy
Net, enduringly can extract the fuel of the amount of needs in longer period from the fuel network.If necessary in fuel network and
Additional gas compressor is also accessed between fuel pipe system, can be really reliably to be lifted the supply pressure of fuel network
Protect the high numerical value of the safe operation of gas turbine.Here, the fuel pressure needed when being fed in combustor is higher than by firing
The pressure ratio that the compressor of gas-turbine is provided.Therefore, adjustable pressure drops so that fuel is also flowed in combustor really.By firing
Supply pressure that is that material net is provided or being provided by additional gas compressor even can be far above the pressure provided by compressor
Than because needing larger numbers of pilot fuel especially when rotor accelerates to running speed and when removal of load, so as to steady
Determine main flame and reliably avoid undesirable thermoacoustics vibration and fray-out of flame.Produce the flame being pre-mixed to ignite
The so-called ignition burner that is pre-mixed of burner has smaller venthole, the smaller outlet in addition
Hole causes to need to continue to improve already very high gas supply pressure, to reach the quality stream of igniting of needs.This with i.e.
Contradict the requirement that also effectively can be run when reducing supply pressure in fuel network.
Content of the invention
It is therefore an object of the present invention to provide a kind of method for running gas turbine, a kind of be used for gas turbine
The device that is adjusted of operation and generating equipment, even if having in fuel network, be only slightly higher than can be by the compression of gas turbine
During the minimum supply pressure of the maximum pressure ratio that machine is produced, methods described or described device guarantee safe operation.
Purpose for the method for running gas turbine is realized by means of the method according to the invention.For described
The purpose of device is by means of realizing according to assembly of the invention.With regard to the purpose for generating equipment, by means of according to this
Bright generating equipment is realizing.
For all solutions are common, the present invention is based on following ideas, and the idea is proposed for special operation
State, such as startup, fuel transformation, removal of load etc., only short time need to improve such as Material collecting box for harvesting in fuel reservoir
In fuel mass flow or only the short time needs to improve fuel pressure, then improve pressure ground if necessary by the fuel matter
Amount stream is transported to the fuel extracted from fuel network.Preferably, when the method according to the invention is implemented, only identical fuel gas
Flock together.First assessment is illustrated, even if the fixed combustion gas of the power between 100 MW and 400 MW can exported
About 1m in turbine3-3m3Case size be enough to be used in the fuel quantity for storing needs under corresponding pressure.There is a small amount of conveying
The simple gas compressor of amount is enough to be used in forming pressure in fuel reservoir, because generally for filling fuel reservoir
Time enough is provided.Such gas compressor ratio enduringly must provide total on high stress level in run duration
The fuel compressor reducer of fuel mass flow is favourable and reliable many times.
With up to now, known mode is on the contrary, also can by means of gas turbine of the present invention from the prior art
Run safely and reliably with the smaller supply pressure in fuel network.Even if in special running status " startup ", " combustion
When material transformation " and " removal of load ", the fuel mass flow for being particularly useful for the additional needs of one or more ignition burners is engaged in
Extract in the fuel reservoir that is first filled with volume of fuel by means of simple gas compressor.Certainly, volume of fuel is in this thing
First extract from fuel network.
The measure of proposition substantially reduces the requirement of the supply pressure in fuel network.By cancelling when fuel mass flow is high
Fuel compressor reducer for the high fuel pressure of comparison can be saved and be bought this high performance fuel compressor reducer
High expense, the high expense of the operation of the fuel compressor reducer during on the other hand saving for gas turbine operation.
Favourable design is given below.
According to the first advantageous approach feature, the volume of fuel in fuel reservoir has than the supply pressure in fuel network
The pressure of Li Genggao.Advantageously, the pressure in volume of fuel is twice as to four more than the supply pressure in fuel network
Times.Thereby it is ensured that the burning that volume of fuel can be conveyed to immediately and with enough sizes in combustor if necessary.For
Realized, fuel can be extracted by fuel compressor during gas turbine operation and/or during fuel network stops
And it is encased in fuel reservoir.Because thus providing sufficiently large time interval for loading fuel reservoir, it is possible to
Using the fuel compressor having than relatively low power.
Additionally, methods described is preferably proposed, in order to briefly improve an ignition burner or many via gas turbine
Individual ignition burner is transported to the pilot fuel flow of combustor, the volume of fuel extracted from fuel reservoir is transported to still treat defeated
Give the pilot fuel of combustor.Especially, therefore, it is possible to avoiding undesirable and unstable fired state.
When provide other fuel types as fuel reservoir in volume of fuel come replace from fuel network extract fuel
When, the probability for thus existing is that fuel reservoir is preferably designed for the form of one or more gas bombs.This eliminates needs
Using fuel compressor.Additionally, by means of more to be conveyed than other fuel types continuation improvement that fuel to be conveyed is more easy to react
Fuel burning-up.The coefficient of efficiency of the burning of this raising, therefore reduces the heat input that generally needs that is hot merit
Rate.Because natural gas or synthesis gas are used as fuel gas most of the time, the fuel for being more easy to react is, for example, hydrogen or acetylene.Easily
Reactivity can be described by the shorter ignition delay time.As in fuel, the easily share of the volume of fuel of reaction is carried
Height, not only flame propagation velocity is improved but also the ignition delay time reduces.Therefore, represent can be by being mixed into hydrogen for two eigenvalues
Or considerably more rapid and greater compactness of burning realized by acetylene, this caused to burn out in time of staying for being given in steam in a combustion chamber
Improvement.Here confirms, in the The fuel stream for conveying altogether, the volume share of 10% to 30% fuel for being more easy to react
Improve thermal effective coefficient enough and amounted to and discharge less unburned fuel, especially unburned Hydrocarbon and
Carbonoxide.Finally, be particularly suited for pilot combustion, when main burning for example in the case of removal of load approximate or
When stopping completely.Meanwhile, under the quality stream for being given of (igniting) The fuel stream, the improvement that heat burns out can realize the totality that burns
Upper more stable thermoacoustics characteristic.
Preferably, in the gas turbine for producing energy, the rotor of gas turbine is operationally coupled to electromotor
On, wherein electromotor is itself coupled to electric current distribution on the net.In this application, removal of load is interpreted as that appearance is produced by electromotor
The unexpected reduction of electrical power, or even it is interpreted as that electromotor is separated with electric current distribution net, that is to say, that produced by electromotor
Electrical power is reduced to suddenly zero.Generally, this removal of load is unexpected and therefore only occurs under failure condition.Fixed
Gas turbine also can simulate this removal of load when bringing into operation, so as to ensure reliable before commercial operation for the first time
Ground and safely operation gas turbine.
According to the present invention, in order to implement preceding method and its preferred implementing form is provided with for entering to the operation of gas turbine
The device that row is adjusted, described device include：
- input, represents the signal for needing additional fuel and/or gas supply pressure not enough in special running status
The input can be transported to,
- outfan, the signal control executive component of the outfan, can be by can be from fuel by means of the executive component
The volume of fuel that bin is extracted is transported to fuel, and
- according to the unit of input signal controlled output signal.According to the present invention, generating equipment includes at least one combustion gas wheel
Machine and the fuel reservoir and being transported to volume of fuel that can be filled with volume of fuel can be persistently extracted from fuel network
The mechanism of fuel.
Preferably, aforementioned mechanism includes the pipeline for being connected fuel reservoir with pipe sections, arranges in the pipeline
Have for opening and closing the executive component of pipeline.In order to avoid the compression shock in the The fuel stream being brought together, in combustion
At least one ejector pump can be provided with pipe material system, can be using the fuel that can persistently extract from fuel network as to be advanced
Medium is transported to the ejector pump and described using being transported to as propulsive medium from the volume of fuel that fuel reservoir is extracted
Ejector pump, wherein corresponding ejector pump are connected with least one burner of gas turbine on the output side.
Description of the drawings
The present invention is expanded on further by means of the embodiment illustrated in accompanying drawing.It is shown specifically：
Fig. 1 illustrates the first embodiment of the fuel system of generating equipment,
Fig. 2 illustrates the design of the alternative of the fuel system with ejector pump of generating equipment, and
Fig. 3 illustrates the fuel reservoir being made up of gas bomb with the volume of fuel for being used for being more easy to react of generating equipment
Fuel system another alternative design.
Specific embodiment
Fig. 1 illustrates the generating equipment 42 with gas turbine 40.The gas turbine include axial configuration compressor 44,
One or more combustor 46 and the turbine unit 48 for equally being constituted with axial configuration.In 40 run duration of gas turbine,
Surrounding air is aspirated by compressor 44 via suction channel 50 and is fed in combustor 46 as the compressed air that has compressed.
Not only by pilot fuel flow and also by main fuel flow via one or more burners or a combustor 46 level or multiple combustions
Burn the level conveying of room 46, and combine the surrounding air that compressed and burn into steam, the steam in turbine unit 48
Expanded in the way of doing work on the rotor 51 of gas turbine 40.The rotor drives the electromotor 52 for coupling thereon, for
Produce electric energy.
The gas turbine 40 of generating equipment 42 is connected with fuel network 13 via fuel system 10.Fuel network 13 can be carried
The fuel gas of the amount for needing, enduringly to run gas turbine 40 under rated load.In detail, except other do not show
Beyond the component for going out, fuel system 10 includes the first fuel channel 12, the input of first fuel channel and fuel network
13 connections.The first valve 14 is provided with the first fuel channel 12 as safety interlock system.In the downstream of the first valve 14 by
One fuel channel 12 is divided into two pipe sections 16,18.First pipe sections 16 be the part of main fuel supply system and
Guide the second valve 20 into, be capable of the volume of the main fuel quality stream of regulating gas turbine 40 by means of the second valve.Second pipe section
18 are the parts of pilot fuel supply system and guide the 3rd valve 24 into via first check-valve 22, by means of the 3rd valve energy
The body of enough pilot fuel quality streams for adjusting the ignition burner or multiple ignition burners that can guide gas turbine 40 into
Product.
In the load point 27 in the downstream of check-valves 22, another fuel channel 26 is led in pipe sections 18.Described another
Locking-valve 28 and decompressor 29 is provided with one fuel channel 26.The end of the inflow side of fuel channel 26 with have as fuel tank
Such as 2m3The fuel reservoir 30 of volume connect.Via the supply pipe for being wherein in series with gas compressor 34 and check-valves 36
Road 32 can be possible to be used as from fuel network 13 fuel of volume of fuel BV in special running status and be transported to fuel storage
Device 30.The use of decompressor 29 makes the compensation of the pressure oscillation when locking-valve 28 is opened become easy.
According to the design of the alternative shown in figure 2 of fuel system 10, the fuel system is in feedback
There is ejector pump 38 on the position of access point 27, can be by the volume of fuel BV that can be stored in fuel reservoir 30 via pipeline 26
The ejector pump is transported to the valve 28 being provided with as propulsive medium, so as to improve in flow ipe section 18 with than
The gross pressure of the fuel B of less pressure.
During gas turbine 40 starts, when fuel changes and/or in removal of load, in order to stable in gas turbine 40
Combustor 46 in the burning that carries out, two forms of implementation for illustrating in fig 1 and 2 are worked in a similar manner, and this is below
Described in.
Before gas turbine is started or after volume of fuel BV being extracted from fuel reservoir 30, run gas compression
Device 34, to fill fuel reservoir 30 with volume of fuel BV (again).Additionally, the fuel body being stored in fuel reservoir 30
Product BV has the high pressure of the comparison that provides in advance, and the pressure is more than the supply pressure in fuel network 13 or more than can be by compressing
The maximum pressure ratio that machine 44 is provided, is its many times such as 3 times.
During gas turbine 40 starts, the rotor 51 of the gas turbine by means of unshowned tumbler or by
Fire speed is accelerated in electromotor 52.Valve 14,24 is subsequently at least opened, and lights pilot flame, so that in combustor
Burnt in 46.Then, the second valve 20 is opened, so that starting main burning.Subsequently, by the lasting liter of fuel mass flow
Height, rotor accelerate to running speed.Furthermore it is possible to reliably avoid the combustion instability for occurring during this period, reach working as
During corresponding rotating speed or directly after corresponding rotating speed is reached, the volume of fuel BV that additionally extracts from fuel reservoir 30 together with
Fuel B extracting from fuel network 13, flowing in second pipe section 18 is for example transported to combustor 46 via ignition burner.
In the case, especially substantial amounts of fuel B can be fed in combustor 46 by means of extra high pressure, until exceeding phase
The rotating speed that answers.Based on the pilot fuel quantity for so increasing, the stable flame produced by ignition burner.Meanwhile, reliably avoid
Undesirable thermoacoustics vibration and fray-out of flame.
In order to avoid in the second pipe section 18 of 24 upstream of valve, pressure is improved suddenly, it is necessary to corresponding lentamente opening valve
28.The fuel stream BS through valve 24 is also fed from fuel reservoir 30, until its reduced pressure is in second pipe section 18
Present in standard supply pressure.
In removal of load, most fuel valves or whole fuel valves of main burner are generally closed forthwith or as far as possible,
Excess rotating speed is accelerated to be avoided as much as rotor, the fuel valve of ignition burner is in order that gas turbine continues on the contrary
Run and stay open.If must in a planned way or unexpectedly carry out removal of load when gas turbine 40 brings into operation, then
The one or more pilot flames in one or more combustor 46 can be stablized, its mode is, when removal of load or straight
Gaseous volume of fuel BV is extracted by opening valve 28 from fuel reservoir 30 after being connected on removal of load, and be transported to stream
Enter fuel B in second pipe section 18, extracting, the combustion being therefore brought together in the downstream of load point 27 from fuel network 13
The pressure P of stream BS is improved.The raising of pressure causes the big fuel quantity in flowing in combustion chamber 46, and this has stable effect.
Additionally, when being provided with fuel and changing in 40 run duration of gas turbine, it is also possible to implement preceding method.Turn in fuel
During change, gaseous main fuel is transformed into from the main fuel of liquid or is changed on the contrary.Continue about 30 seconds to about for described
The transformation process of 180 seconds needs the stable burning of pilot flame, and this is only by the volume of fuel BV of additional penetrating during which
To reach.For this respect, by pressure is improved in fuel by means of interpolation volume of fuel BV, only shortly carry out fire
Flame stable operation.After fuel changes, routinely can continue to run with without volume of fuel BV.
According to the design according to Fig. 2, the volume of fuel BV in fuel reservoir 30 is stored in as fuel B
, flow into second pipe section 18 and the initial propulsive medium work that extracts from fuel network 13.By fuel B in ejector pump 38
The fuel stream BS is gathered into volume of fuel BV, so that described two The fuel stream B, BV collective effects are in ejector pump 38
Realize that the pressure for needing is improved in pipe sections 18 in downstream.By using ejector pump 38, fuel reservoir 30 can be smaller
Constitute.Thus, when valve 28 is opened, it is also possible that in 24 upstream of valve, substantially gentler pressure is improved.Thus, valve 28 can
Constitute particularly simple and then at low cost as far as possible.If necessary, valve 28 can also be configured to distributing valve so need not
Regulating valve.
The control of valve 28 is carried out by means of device 60.60 one side of device has input E, represents the need of additional fuel
Ask or the signal of gas supply pressure deficiency can be transported to the input.Preferably, gas turbine rotor 51 is herein related to
Current rotating speed, represent gas turbine 40 load condition or fuel change signal.Additionally, device 60 includes outfan 62,
The signal control executive component of the outfan, preferred valve 28, can be by can be from fuel reservoir by means of the executive component
The 30 volume of fuel BV for extracting are transported to the fuel B flowed in second pipe section 18.Additionally, device 60 is included according to input letter
The unit of the method controlled output signal that number basis is given.
According to the embodiment according to Fig. 3 and with differently 30 structure of fuel reservoir of the embodiment according to Fig. 1
Make as a gas bomb or the group of multiple gas bombs 64 in parallel.Ratio has been stored in the gas bomb 64 to carry from fuel network 13
The fuel B for taking substantially is more easy to the fuel for reacting for use as volume of fuel BV.For example, hydrogen and acetylene are stored in gas bomb 64.
These fuel can be added to the fuel B extracted from fuel network 13 as the volume of fuel BV under aforesaid applicable cases, with
Burn out for improving and stably burn for thermoacoustics.
The embodiment illustrated in Fig. 1,2 and 3 is used merely to explain the present invention and does not limit the present invention and also can be each other
Combination.So enable in particular to be provided with multiple combustor 46, the combustor includes ignition burner respectively and including being respectively provided with
One or more levels main burner, wherein described ignition burner are connected on fuel system 10.Obviously, main burner
The volume of fuel BV extracted from fuel reservoir can be additionally supplied with, so that with approximate during similar running status
Mode stablizes one or more main flames.By means of the example description present invention with fuel gas.However, not forced use
Fuel gas.Obviously, liquid fuel can also be conveyed in the fuel system 10 according to the present invention.Liquid and fuel gas
Combination be also possible, wherein however do not carry out the mixing of liquid and fuel gas in load point 27 or in ejector pump 38,
But carry out the separation of fuel gas and liquid fuel with regard to pilot fuel and main fuel：I.e. pilot fuel can be gaseous
And main fuel can be liquid, or vice versa.
Generating equipment 42 can also include the steam turbine unit further not illustrated, the rotor of the steam turbine unit is same
Sample and the electromotor 52 for illustrating are coupled on the common axle of further referred to as shafting.
Therefore, generally speaking, propose a kind of method for starting gas turbine 40, a kind of be used for by means of the present invention
Removal of load or fuel run the method for gas turbine 40, a kind of dress for being adjusted to the operation of gas turbine 40 when changing
Put 60 and a kind of generating equipment 42.Although the supply pressure of fuel network 13 is only smaller, in order to during starting, get rid of negative
The safe operation of gas turbine 40 being realized during lotus or when fuel changes and being proposed, volume of fuel BV is provided with and fuel network
Supply pressure in 13 compares the pressure for significantly improving, and briefly convey if necessary the fuel B that extracts from fuel network 13 with
For improving the pressure of the fuel.By providing higher fuel pressure, pilot flame can be in the ruuning situation for needing
Under burn in a stable manner.Although the supply pressure enduringly provided by fuel network 13 is less, thermoacoustics can be also avoided
Vibration and fray-out of flame.
Claims (19)
1. the method for being used for running fixed gas turbine (40),
There is following step：
- fuel (B) is constantly extracted from fuel network (13), and
- burning the combustion at least one combustor (46) of the gas turbine (40) in the case where combustion air is added
Material (B), wherein described combustor include main burner and ignition burner,
Characterized in that,
One or more main burners that fuel is transported to gas turbine (40) via the first pipe sections (16), and will combustion
Material is transported to one or more ignition burners via second pipe section (18),
In order to briefly improve a pilot combustion that is being transported to the combustor and then being transported to the gas turbine (40)
The pressure of the pilot fuel flow (BS) of device or multiple ignition burners, the volume of fuel (BV) that will be extracted from fuel reservoir (30)
It is delivered to the pilot fuel still to be delivered to the combustor (46).
2. method according to claim 1,
Wherein
During the gas turbine (40) starts, the pilot fuel flow (BS) is briefly improved when fuel changes
Pressure.
3. method according to claim 1,
Wherein
The pressure of the pilot fuel flow (BS) is briefly improved when removal of load.
4. method according to claim 2,
Wherein
The pressure of the pilot fuel flow (BS) is briefly improved when removal of load.
5. method according to claim 1,
Wherein
The pressure of the pilot fuel flow (BS) is directly briefly improved after removal of load.
6. method according to claim 2,
Wherein
The pressure of the pilot fuel flow (BS) is directly briefly improved after removal of load.
7. method according to any one of claim 1 to 6,
Wherein described volume of fuel (BV) has the pressure higher than the fuel (B) extracted from the fuel network (13).
8. method according to claim 7,
The pressure of wherein described volume of fuel (BV) is twice as to four more than the supply pressure in the fuel network (13)
Times.
9. method according to any one of claim 1 to 6,
Wherein described gas turbine (40) be operationally drivingly connected to electric current distribution net electromotor (52), and wherein due to
Suddenly reduce the electrical power that produced by the electromotor (52) or due to by the electromotor (52) and electric current distribution net
Separate and produce removal of load.
10. the method according to any one of claim 3 to 6,
Wherein described removal of load is unexpected, or is modeled.
11. methods according to any one of claim 1 to 6,
Wherein will from the fuel network (13) extract with the fuel than the supply pressure higher pressure in the fuel network
Volume (BV) is transported to the fuel reservoir (30).
12. methods according to claim 1,
Wherein described fuel reservoir (30) include the combustion for being different from the species of the fuel (B) and providing in gas bomb
Material volume (BV).
13. methods according to claim 12,
Wherein described volume of fuel (BV) is the species that the pilot fuel more to be conveyed than still is substantially more easy to react.
14. methods according to claim 12 or 13,
Wherein described volume of fuel (BV) mainly has acetylene or hydrogen or is made up of acetylene or hydrogen completely.
15. are used for device (60) that the operation of fixed gas turbine (40) is adjusted,
- there is input (E), represent that the signal for needing additional fuel and/or gas supply pressure not enough can be transported to institute
State input,
- there is outfan (62), signal control executive component (28) of the outfan can be by by means of the executive component
Fuel (B) can be transported to from the volume of fuel (BV) that fuel reservoir (30) extract, wherein combustor includes main burner and draws
Burner, and
- with the unit according to input signal controlled output signal,
Characterized in that,
Fuel is transported to one or more main burners of gas turbine (40), and fuel warp via the first pipe sections (16)
One or more ignition burners are transported to by second pipe section (18),
One that is further transported to the gas turbine (40) in order to briefly improve the combustor for being transported to gas turbine draws
The pressure of the pilot fuel flow (BS) of burner or multiple ignition burners, from the fuel reservoir (30) extract described
Volume of fuel (BV) is transported to pilot fuel still to be delivered to the combustor (46).
16. generating equipments (42),
Including the fixed gas turbine (40) with least one combustor (46) and compressor (44), wherein by the pressure
Combustion air and can be transported to the combustor from the fuel (B) that fuel network (13) persistently extract that contracting machine (44) is provided
(46), wherein described combustor includes main burner and ignition burner,
Characterized in that,
It is provided with the fuel reservoir (30) that can be filled with volume of fuel (BV) and is provided with and the volume of fuel (BV) can be conveyed
To the mechanism of the fuel (B) that can persistently extract from the fuel network (13),
Fuel is transported to one or more main burners of gas turbine (40), and fuel warp via the first pipe sections (16)
One or more ignition burners are transported to by second pipe section (18),
In order to briefly improve an ignition burner that is being transported to combustor and then being transported to the gas turbine (40) or
The pressure of the pilot fuel flow (BS) of multiple ignition burners, from the volume of fuel that the fuel reservoir (30) is extracted
(BV) pilot fuel still to be delivered to the combustor (46) is transported to.
17. generating equipment (42) according to claim 16,
Wherein described mechanism includes the pipeline (26) for being connected the fuel reservoir (30) with second pipe section (18),
It is provided with the pipeline (26) for opening and closing the executive component (28) of the pipeline (26).
18. generating equipment (42) according to claim 17,
There is at least one ejector pump (38), the fuel (B) that can persistently extract from the fuel network (13) and as propulsive medium
Can be transported to the ejector pump from the volume of fuel (BV) that the fuel reservoir (30) extract, wherein corresponding spray
Pump (38) is connected with least one ignition burner of the gas turbine (40) on the output side.
19. generating equipments (42) according to claim 16,17 or 18,
There is device according to claim 15 (60).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP10193135A EP2458181A1 (en) | 2010-11-30 | 2010-11-30 | Method for operating a gas turbine during load control, device for regulating the operation of a gas turbine and power plant |
| EP10193135.0 | 2010-11-30 | ||
| PCT/EP2011/071243 WO2012072614A1 (en) | 2010-11-30 | 2011-11-29 | Method for operating a fixed gas turbine, device for regulating the operation of a gas turbine and power plant |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103237971A CN103237971A (en) | 2013-08-07 |
| CN103237971B true CN103237971B (en) | 2017-03-15 |
Family
ID=43971271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201180057654.2A Expired - Fee Related CN103237971B (en) | 2010-11-30 | 2011-11-29 | Method for running fixed gas turbine, for device that the operation of gas turbine is adjusted and generating equipment |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20130247578A1 (en) |
| EP (2) | EP2458181A1 (en) |
| JP (1) | JP5808819B2 (en) |
| CN (1) | CN103237971B (en) |
| RU (1) | RU2602214C2 (en) |
| WO (1) | WO2012072614A1 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105814295B (en) | 2014-02-19 | 2017-10-31 | 西门子公司 | Fuel supply lines system for gas turbine |
| DE102014216014A1 (en) | 2014-08-13 | 2016-02-18 | Siemens Aktiengesellschaft | Power plant with emergency fuel system |
| US11459959B2 (en) * | 2016-09-16 | 2022-10-04 | General Electric Company | Method for starting a gas turbine |
| EP3301268A1 (en) * | 2016-09-29 | 2018-04-04 | Siemens Aktiengesellschaft | Power plant control in coordination with further energy sources, like renewable energy |
| JP6963512B2 (en) | 2018-01-12 | 2021-11-10 | 三菱パワー株式会社 | Fuel supply systems, gas turbines, power plants, control methods and programs |
| CN111855221A (en) * | 2020-07-28 | 2020-10-30 | 青岛中科国晟动力科技有限公司 | Combustion state monitoring method and system for gas turbine |
| CN114320493B (en) * | 2022-01-14 | 2023-11-03 | 中国能源建设集团浙江省电力设计院有限公司 | Undisturbed switching method between 9H-cascade combined circulating unit booster units |
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| US5533329A (en) * | 1993-05-17 | 1996-07-09 | Hitachi, Ltd. | Control apparatus for and control method of gas turbine |
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-
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- 2011-11-29 CN CN201180057654.2A patent/CN103237971B/en not_active Expired - Fee Related
- 2011-11-29 RU RU2013129536/02A patent/RU2602214C2/en not_active IP Right Cessation
- 2011-11-29 US US13/990,098 patent/US20130247578A1/en not_active Abandoned
- 2011-11-29 EP EP11791264.2A patent/EP2646668A1/en not_active Withdrawn
- 2011-11-29 JP JP2013541321A patent/JP5808819B2/en not_active Expired - Fee Related
- 2011-11-29 WO PCT/EP2011/071243 patent/WO2012072614A1/en active Application Filing
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| US5533329A (en) * | 1993-05-17 | 1996-07-09 | Hitachi, Ltd. | Control apparatus for and control method of gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20130247578A1 (en) | 2013-09-26 |
| EP2646668A1 (en) | 2013-10-09 |
| RU2602214C2 (en) | 2016-11-10 |
| RU2013129536A (en) | 2015-01-10 |
| CN103237971A (en) | 2013-08-07 |
| JP2013545022A (en) | 2013-12-19 |
| EP2458181A1 (en) | 2012-05-30 |
| JP5808819B2 (en) | 2015-11-10 |
| WO2012072614A1 (en) | 2012-06-07 |
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